Second Stage Compressor Stator Vane Airfoil Profile Optimization
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Solution Overview
Problem
Current compressor stator vane designs in multi-stage axial compressors do not fully optimize airfoil profiles for specific stages, leading to suboptimal compression efficiency and performance.
Innovation Solution
The development of airfoil profiles with specific Cartesian coordinate values for suction and pressure sides, optimized for specific stages of multi-stage axial compressors, which define airfoil sections and shapes to enhance compression efficiency and adaptability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If a generic airfoil profile is used for compressor stator vanes, then manufacturing and design are simplified, but compression efficiency and stage-specific performance deteriorate
Solution Approach 1:
The patent applies local quality by providing different airfoil profile coordinate values for different compressor stages. Each stage (first stage, second stage, third stage, etc.) has its own optimized suction side and pressure side coordinate values, allowing each local region (stage) to have properties tailored to its specific flow conditions and performance requirements, thereby resolving the contradiction between design simplicity and compression efficiency.
2Productivity
If stage-specific airfoil profiles are optimized, then compression efficiency improves, but design complexity and data requirements increase
Solution Approach 1:
The patent applies parameter changes by systematically varying the airfoil profile parameters (suction side coordinate values and pressure side coordinate values) for each compressor stage. This allows optimization of compression efficiency through parameter adjustment while maintaining a consistent methodology and data structure across all stages, thereby managing design complexity through systematic parameterization rather than ad-hoc design.
Data Source
AI summary
A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.